Rolls-Royce Corporation

Jade Whittle

Richard G Mochrie

Graeme E F Sutcliffe

Michael J Whittle

A ram-air duct system includes a ram-air duct configured to receive a flow of ram-air from a ram-air inlet and discharge the flow to a ram-air outlet. The system also includes a heat exchanger configured to exchange heat with air within the ram-air duct, an auxiliary air passageway and an electrically-driven air mover configured to move a flow of auxiliary air along the auxiliary air passageway for discharge into the ram-air duct through an intermediate inlet between the ram-air inlet and the ram-air outlet. The air duct system further includes a controller configured to selectively operate the ram-air duct system in an auxiliary supply mode in which the air mover and/or a control valve are controlled to cause the flow of auxiliary air to be discharged into the duct through the intermediate inlet, to thereby control a rate of heat exchange between the heat exchanger and air within the duct.

Ram-air duct system

A fuel management system for a gas turbine engine, the fuel management system comprising a fuel supply line configured to supply fuel from a system inlet to a combustor of the gas turbine engine via a combustor pump and combustor valve. A heat exchanger is configured to reject heat from a thermal load of the gas turbine engine to fuel in the fuel supply line between the system inlet and the combustor valve. There is a downstream recirculation line configured to recirculate a downstream excess portion of fuel from the fuel supply line, the downstream recirculation line extending from a downstream recirculation point on the fuel supply line between the heat exchanger and the combustor valve.

Fuel management system

A gas turbine engine comprising a combustor and a fuel management system. The fuel management system comprises a fuel supply line, recirculation line and heat exchanger. The fuel supply line is configured to supply fuel to the combustor. The recirculation line is configured to recirculate excess fuel from the fuel supply line to an engine-located fuel tank via a fuel cooling device. The fuel cooling device is configured to reject heat from the excess fuel in the recirculation line. The heat exchanger is configured to reject heat from a thermal load of the gas turbine engine to fuel in the fuel management system. The heat exchanger is disposed on the fuel supply line or on the recirculation line. The fuel supply line is configured to receive fuel from an external source and from the engine-located fuel tank.

Gas turbine engine with a fuel management system

A turbine assembly according to the present disclosure includes ceramic matrix composite vanes mounted to a metallic case. The turbine assembly includes a turbine case cooling system with a vane case cooling unit configured to manage the temperature and diameter of the metallic case at the location where the ceramic matrix composite vanes are mounted so as to control circumferential movement of the vanes relative to one another during heating and cooling of the turbine assembly when used in a gas turbine engine.

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Bristol, United Kingdom

Jade Whittle